Air cooled in-line engine



2 Sheets-Sheet'l INVENTOR ATTORNEY BY DELMER 5. FAHRNEY fl rmllfw Jan. 31, 1939. D. s, FAHRNEY- AIR COOLED IN-LINE ENGINE Fi] ed Jan.

Jan. 31, 1939. D. s. FAHRNEY AIR COOLED IN-LINE ENGINE Filed Jan. 19, 1938 2 Sheets-Sheet 2 INVENTOR DELMER S. FAHRNEY' ATTORNEY Patented Jan. 31, 1939 I UNITED STATES PATENT OFFICE AIR COOLED IN-LINE ENGINE Delmcr S. Fahmey, United States Navy Application January 19, 1938, Serial No. 185,675

I 2 Claims. (Cl. 244-55) (Granted under the act of March 3, 1883, as amended April 30, 1928; 370 0. G. 757) This invention relates to an air cooled in-line water cooled engine 23 is conducted through the engine, particularly intended for use on aircraft, concentric shafts 24 to the twin propellers 25. and has for an object to provide an in-line engine In Figs. 4 and 5 the engines 33 are shown as either of the straight type or of the v type being mounted in the leading edge 34 of a ver- 5 which may be cooled by air instead of necessitical strut 35, the aircraft wing being shown at 5 tating liquid cooling means, as customary. 36. In this case the cowlings 31 are mounted on A further object of this invention is to proshafts 38 journaled in suitably positioned brackvide a means for controlling the amount of air ets 39. In this case both engines 33 are shown cooling to which the in-line engine of this inas being mounted below the propeller gearing 40 vention is exposed. I to the propeller shafts 4| and twin propellers 42. 10

A further object of this invention is to pro- As a result of this invention air cooled in-line vide an air cooled in-line engine which may be engines may be provided in horizontal or v'ermounted either horizontally or vertically, and tical arrangement on aircraft of any size, and in V likewise may be mounted in multiple units, large aircraft the several types of mountings may geared together either for operating a single be used simultaneously in conjunction with liquid 15 propeller or for operating a pair of twin propele cooled engines as well. In the air cooledengine lers revolving in adjacent planes. the space between the forward edges of the cowl- With the foregoing'and other objects in view, ings'provides the leading opening for the air to the invention consists in the construction, comreach the engine. By opening the cowlings the bination and arrangement of parts hereinafter air is permitted to escape from the engines more 20 described and illustrated in the drawings, in rapidly, and hence may enter the leading openwhich, ing more rapidly.

Fig. l is a top elevational view of an installaother modifications and changes in the protion of this invention in the leading ed of an portions and arrangements of the parts may be aircraft wing, partly broken away; made by those skilled in the art without departs a Sec o V ew On l ne of ing from the nature of the invention, withinthe 25 Fig. 3 shows a view similar to Fig. 2 of another scope (it what is hereinafterclaimed.

adaptation of this invention; The invention described herein may be manu- Fig. 4 is an elevational view of a vertical infactured and d by o for th G v rnm nt of stallation of this inventi n; n the United States of America for governmental Fig. 5 is a sectional view on line 55 of Fig. 4. purposes t t t payment 1 any royalties 30 There is shown at l0 an aircraft wing pr othereon or th f vided with the usual box Spar H adjacent lts Having thus set forth and disclosed the nature i edge A i engine as of this invention, what is claimed is:

bemg of the V type 15 mounted on Pracket 1. In combination, an air cooled in-line engine 35 secured tqthe Spar the space m the box ,mounted on a leading edge of an aircraft, and spar H bemg utilized as a protective passage for cowling means for controlling cooling air to the the fuel lines, oil lines, enginecontrols, etc., to engine, said cowling means comprising a pair of the engme' cowling flaps, each flap being journaled at its 40 As Shown m g pair of engines are leading edge forward of the engine, the leading 40 mounted with their crankshafts l5 operating a edges of the cowling flaps being Spaced apart to common qlfierential gearing. on propengr Y provide an air entrance, said cowling flaps overshafhn loumalgd in bearmgs segm-ed m lying said engine on opposite sides thereof. brackets l9 and tubular struts 20. Cowhng flaps In combination an m r cooled mdme engine fixed on shafts n t Journaleg m brackets mounted on a leading edge of an aircraft, and 45 and wing strut 43 within the leading edge II, the cbwling means for controlling cooling air to the ggg i z g ggg g gi gggagi bemg Omltted m engine, said cowling means comprising a pair Suitable remote control means, not shown, may of cowling flaps, each flap being journaled at its be provided for regulating the degree of opening lea-ding edge mmfard the engine the leading 50 of the flaps 2| in the directions of the positions edges of the ling flaps being spaced apart to 2| so as to regulate the amount of air that me provide an a r ntra sa d cowling flaps v rflow over the engines l3 to cool them. l g said engine, S rlyin edges being In Fig. 3 a water cooled in-line engine 23 has movable a y from a d engines to ase t e been shown behind the differential gear box l6, air. exit therefrom.

66 and power from the air cooled engine l3 and DELLIER S. FAHRNEY. 

